Disc Turbo Charger

Abstract

A disc turbocharger includes a multi-disc engine in which each disc engine includes a turbine blade, a compressor blade, and a bearing without requiring a shaft between the turbine blade and the compressor blade. The power produced by each turbine blade is consumed by its own joined compressor. The disc turbocharger has a multi-disc engine that works as a multi-stage turbocharger with a smaller size and no piping between the turbochargers. The disc turbocharger uses a waste spool valve for control of the.

Claims

1. A disc turbocharger defining an axial direction comprising: a rotational axis with at least one disc on a shaft; a compressor chamber having at least one compressor blade section and a turbine chamber having at least one turbine blade section; a nozzle located in front of a first turbine blade in said turbine chamber; a compressor blade placed in axial flow to an inlet, wherein said at least one disc comprises: a core bearing, surrounded by said compressor blade, arranged radially outward of said core bearing; each of said at least one turbine blade section is joined to the at least one compressor blade section and is surrounding and radially outward of the at least one compressor blade section, and an inlet exhaust gas chamber located before a first turbine in said at least one turbine blade section and an outlet exhaust chamber located after a last turbine in said at least one turbine blade section; said turbine further includes a first outlet port, and a second outlet port that both connect to an exhaust gas valve, and wherein an inlet air chamber is located before said compressor blade in said at least one compressor blade section and an outlet air compressed chamber is located after a last compressor in said at least one compressor blade section, and wherein said exhaust gas valve controls said disc turbocharger to turbocharge an internal combustion engine.

2. The disc turbocharger according to claim 1, wherein said shaft has a first channel that feeds oil through said core bearing, and a second channel that returns the oil from said core bearing to an oil pump of said internal combustion engine.

3. The disc turbocharger according to claim 1, wherein said disc turbocharger has at least two discs and there is no stator between each of said at least one disc.

4. (canceled)

5. The disc turbocharger according to claim 1, wherein said core bearing is an oil bearing.

6. (canceled)

7. The disc turbocharger according to claim 1, that further includes a double wall between said compressor chamber and said turbine chamber, and said double walls includes an air bleed from said compressor chamber into a space between said double wall.

8. (canceled)

9. The disc turbocharger according to claim 1, wherein said at least one-disc includes more than one disc within said disc turbocharger and each of said discs runs freely and individually from each other disc and each said disc runs in alternate directions of rotation of each adjacent said disc and each said disc acts as a stator to each adjacent said disc and does not have a separate stator between stages of each at least one compression blade section or each of said at least one turbine blade section.

10. (canceled)

11. The disc turbocharger according to claim 1, wherein said exhaust gas valve is a waste spool valve.

12. The disc turbocharger according to claim 11, wherein said waste spool valve includes a two-piston valve, a stem, at least two inlet ports and a single outlet port from said waste spool valve for exhaust gas, a compressed air inlet port, and a spring to balance pressure to control said waste spool valve, and said two-piston valve includes a thermal insulator and compression rings.

13. A disc turbocharger defining an axial direction comprising: a rotational axis with at least one disc on a shaft; a compressor chamber having at least one compressor blade section and a turbine chamber having at least one turbine blade section; a nozzle located in front of a first turbine blade in said turbine chamber; a compressor blade placed in axial flow to an inlet, wherein said at least one disc one disc comprises: said shaft, surrounded by said at least one compressor blade, arranged radially outward of said shaft; each of said at least one turbine blade section is joined to the at least one compressor blade section and is surrounding and radially outward of the at least one compressor blade section, and an inlet exhaust gas chamber located before a first turbine in said at least one turbine blade section and an outlet exhaust chamber located after a last of turbine in said at least one turbine blade section; said turbine further includes a first outlet port, and a second outlet port that both connect to an exhaust gas valve, and wherein an inlet air chamber is located before a first compressor in said at least one compressor blade section and an outlet air compressed chamber is located after a last compressor in said at least one compressor blade section, and wherein an exhaust gas valve controls said disc turbocharger to turbocharge an internal combustion engine.

14. (canceled)

15. (canceled)

16. The disc turbocharger according to claim 13, wherein said shaft of said at least one disc is coupled to an engine shaft of the internal combustion engine through a transmission and said disc turbocharger acts as a supercharger and said first turbine blade in said disc turbocharger produces additional torque from exhaust gas of said-internal combustion engine to act as a turbine engine.

17. The disc turbocharger according to claim 16, wherein said transmission includes planetary gears.

18. The disc turbocharger according to claim 16, wherein said transmission is a continuously variable transmission.

19. The disc turbocharger according to claim 16, wherein said transmission is a gear box.

20. A disc turbocharger defining an axial direction comprising: a rotational axis with at least one disc on a shaft; a compressor chamber having at least one compressor blade section and a turbine chamber having at least one turbine blade section; a nozzle located in front of a first turbine blade in said turbine chamber; a compressor blade placed in axial flow to an inlet, wherein said at least one disc comprises: said shaft, surrounded by said at least one turbine blades arranged radially outward of said shaft; each of said at least one compressor blade are surrounding and radially outward of each joined at least one turbine blade, and an inlet exhaust gas chamber located before a first turbine in said at least one turbine blade section and an outlet exhaust chamber located after a last of turbine in said at least one turbine blade section; said turbine further includes a first outlet port, and a second outlet port that both connect to an exhaust gas valve, and wherein an inlet air chamber is located before a first compressor in said at least one compressor blade section and an outlet air compressed chamber is located after a last compressor in said at least one compressor blade section, and wherein an exhaust gas valve controls said disc turbocharger to turbocharge an internal combustion engine.

Description

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING(S)

[0019] FIG. 1 shows a block diagram of a prior art two stage turbocharger.

[0020] FIG. 2 shows a sectional view of a disc turbocharger.

[0021] FIG. 3 shows a sectional view of the disc turbocharger with two discs operating as two turbochargers.

[0022] FIG. 4 shows a sectional view of the disc turbocharger with three discs.

[0023] FIG. 5 shows a contemplated turbine blade and a compressor blade for a three-disc turbocharger.

[0024] FIG. 6 shows a sectional view of the disc turbocharger as an alternate contemplated embodiment.

[0025] FIG. 7 shows a cross-section of another contemplated embodiment of the disc turbocharger.

[0026] FIG. 8 shows a sectional view of the disc turbocharger in another contemplated embodiment.

[0027] FIG. 9 shows a sectional view of a prior art wastegate valve.

[0028] FIG. 10A and 10B show sectional views of a wastegate spool valve at different stages of operation.

[0029] FIG. 11A-11C show sectional view of the waste spool exhaust valve in operation.

[0030] FIG. 12 shows a cartridge body using a thermal insulator.

[0031] FIG. 13 shows the air bleeding system.

[0032] FIG. 14 shows a sectional view of the disc turbocharger with on disc engine.

DETAILED DESCRIPTION OF THE INVENTION

[0033] FIG. 1 shows a block diagram of a prior art two stage turbocharger on an engine 20 with an intake manifold 21 and an exhaust manifold 22 where each turbocharger has a separate body with one body for the turbine 15, 16 and a second body 17, 18 for the compressor. The two bodies are connected with a shaft or shafts 13, 14. Piping connects the different stages with valve(s) 11 between the two turbochargers and there are one or two wastegate valves 12. This figure also shows an intercooler 19. Air is drawn into 23 the compressor 17 and exhaust 24 exits the last turbine 16.

[0034] FIG. 2 shows a sectional view of a disc turbocharger 30. The disc turbocharger 30 has a shaft 31 and bearing 32 and disk engine 33 that includes a turbine blade 34 and a compressor blade 35. One or more of the compressor blade(s) 35 forms a compressor blade section. One or more of the turbine blade(s) 34 forms a turbine blade section blade section. The compressor blade 35 works as a centrifuge with axial flow. The exhaust gas 36 enters into the inlet chamber G1, then into the nozzle 37, then into the turbine blade 34 blade, then into outlet exhaust chamber G2 and then exits as exhaust gas 38. The outside filtered air 39 goes into inlet air chamber A1 where it is compressed with compressor blade(s) 35, then into outlet air compressed chamber A2 and then to outlet 40 to the engine. There is a spool exhaust valve that controls the system using inlet gas chamber G1, outlet exhaust chamber G2 and outlet air compressed chamber A2 as shown in FIG. 10. There are also air bleed vents 41 that intercools the compressor wall. The outlet port of chamber G1 goes into the spool valve through port 71. The outlet port of outlet exhaust chamber G2 goes to the spool valve through port 72.

[0035] FIG. 3 shows a sectional view of the disc turbocharger with two-disc engines 34 and 44 operating as two turbochargers. A disc engine is a combination of a compressor blade 35, and a turbine blade 34 with or without a bearing 47 connecting the compressor 35 to the shaft 29 or 31. In this embodiment, each disc engine operates independently and in opposite directions of rotation or each other. Each disc is connected to a fixed shaft 29 with bearings 47. The fixed shaft 29 has two oil channels, one channel 50 is for oil to flow into the bearing(s) and one channel 51 is for oil that returns from the bearing(s). The disc turbocharger has a waste spool valve, shown in FIGS. 11. To overcome turbo lag at low flow of the exhaust gas, only one disc 34 engine turns T2, and the exhaust gas will bypass T1 the second disc 44 through the port 72 at G2 to port 73 at G3 and through the waste spool valve as shown in FIG. 11. At high exhaust flow rates, the waste spool valve will close the port 72 at G2 and the exhaust gas will not be bypassed and the two-disc engines will work 34, 44. At higher exhaust flow rates, for safety of the combustion engine, the exhaust gas will partially bypass the two disc-engines 34, 44 as shown in FIG. 11.

[0036] FIG. 4 shows a sectional view of the disc turbocharger with three discs 34, 44 and 54. This embodiment is similar to the disc turbocharger shown and described in FIG. 3, and operates with higher exhaust vehicles such as diesel engines.

[0037] FIG. 5 shows a contemplated turbine blade 34, 44 and 54 and a compressor blade for a three-disc turbocharger. The speed of each disc runs at a different speed to make the turbocharger more efficient.

[0038] FIG. 6 shows a sectional view of the disc turbocharger as an alternate contemplated embodiment. This turbocharger has a one-disc engine with a shaft 31 that is coupled to a flywheel 60 with a one-way clutch 61 and a gear 62 or similar transmission. To overcome turbo lag at low exhaust flow rates, the flywheel and the disc turbo engine turn together as a supercharge and any extra torque is transferred from the turbine blade to the engine. At higher exhaust flow rates, the disc engine can run faster than the flywheel and the disc engine is decouple from the flywheel through a one-way clutch. In this mode, the disc turbocharger operates as a turbocharger.

[0039] FIG. 7 shows a cross-section of another contemplated embodiment of the disc turbocharger. This is a variation of the embodiment shown in FIG. 6. The disc is connected with one or more planetary gears 65 to the engine with a one-way clutch 61 or without a one-way clutch 61 as previously shown and described in FIG. 6. The gears 65 are a transmission, while gears are shown and disclosed, other forms of a transmission are contemplated, including but not limited to planetary gears, continuously variable transmission and a gear box.

[0040] FIG. 8 shows a sectional view of the disc turbocharger in another contemplated embodiment. This embodiment uses an electrical motor 70 for assisting the turbocharger at low exhaust flow rates. At higher exhaust flows the electric motor will be disconnected from the power supply by the engine controller and the electrical motor shaft is decoupled from the disc turbocharger shaft using a one-way clutch 61.

[0041] FIG. 9 shows a sectional view of a prior art wastegate valve 80. The exhaust gas 81 will bypass the turbocharger by using the poppet valve 82, in which the valve comprises a valve head 83 in a valve seat 84, the valve head 83 is carried by a valve stem 85 that is mounted in a valve guide. A spring 86 is provided to bias the valve into a closed position. The valve head 83 is exposed to pressure of the exhaust gas 81 upstream of the turbine itself in such a way that pressure of the exhaust gas 81 acts on the poppet valve 82 in a direction to open the valve. When the pressure of the exhaust gas 81 overcomes the pressure of the spring 86, the valve opens and a portion of the exhaust gas 81 bypasses the turbine to further limit an increase of speed and pressure from the turbine and compressor.

[0042] A problem arises in poppet valves 82 as the exhaust 81 pressure pulsates. The peak value of the exhaust pressure pulses, either directly or when superimposed in the pressure of the supply of operating fluid, approximately balance the pressure of the spring 86, this causes the valve to open and close very rapidly and may continue throughout all open conditions of the valve. Valve oscillation in turn causes rapid wear.

[0043] FIG. 10A and 10B show sectional views of a waste spool valve at different stages of operation. This style of exhaust gas valve operates independently of the exhaust gas pressure. The only two elements that control the valve are the spring 96 load and the high pressure of the air after the compressor 93. The spool valve includes a two-piston 91, 92 with a cartridge body using a thermal insulator with compression rings, the high pressure compressed air A2 will balance the spring 96 load. At low pressure there is no bypass to the exhaust gas for the system. The port 71 of exhaust gas before the turbine 34 is closed. At high pressure compressed air 93 pushes the piston 92 to open the port 71 before the turbine 34 to the port 72 after the turbine of turbocharger 34 for bypassing the exhaust gas. This waste spool valve bypasses one-or-more disc engines.

[0044] FIG. 11A-11C show sectional views of the waste exhaust valve in operation to control two-or-more disc engines. At a low exhaust flow rate, only one-disc engine is turning T1 and exhaust gas bypasses the second disc engine T2. The bypass of the exhaust gas is from port 72 to port 73 as shown in FIG. 11A. As soon as exhaust pressure builds it will push 93 the spool valve to close port 72 and there will be no bypass of any exhaust gas to the two-disc engine in operation as seen in FIG. 11B. When the exhaust pressure builds very high, for the protection of the engine, the waste spool valve will open the port 71 to port 73 further and the exhaust gas will bypass the two-disc engine for protection as shown in FIG. 11C.

[0045] FIG. 12 shows a cartridge body using a thermal insulator 92 which also acts as a seal between the two sections and uses a compression ring 97.

[0046] FIG. 13 shows the air bleeding system where the compressed air from outlet air compressed chamber A2 bleeds through a bleed vent hole 41 into a space between the two walls.

[0047] FIG. 14 shows a sectional view of the disc turbocharger with on disc engine. This is smaller in FIG. 2, except the compress section 35 is outside the turbine section 34.

[0048] Thus, specific embodiments of a concentric planar turbo charger have been disclosed. It should be apparent, however, to those skilled in the art that many more modifications besides those described are possible without departing from the inventive concepts herein. The inventive subject matter, therefore, is not to be restricted except in the spirit of the appended claims.

Sequence Listing

[0049] Not Applicable.